IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0214302
(2005-08-29)
|
등록번호 |
US-7467922
(2008-12-23)
|
발명자
/ 주소 |
- Beeck,Alexander Ralph
- Irmisch,Stefan
|
출원인 / 주소 |
- Siemens Aktiengesellschaft
|
인용정보 |
피인용 횟수 :
13 인용 특허 :
2 |
초록
▼
The invention relates to a turbine blade or vane for a gas turbine, having a blade or vane root, which is successively adjoined by a platform region with a transversely running platform and then a blade or vane profile which is curved in the longitudinal direction, having a platform surface, which i
The invention relates to a turbine blade or vane for a gas turbine, having a blade or vane root, which is successively adjoined by a platform region with a transversely running platform and then a blade or vane profile which is curved in the longitudinal direction, having a platform surface, which is provided at the platform and can be exposed to hot gas, and having at least one cavity, which is open on the root side, through which a coolant can flow and which extends through the blade or vane root and at least into the platform region and is surrounded by an inner wall, the contour of which, running in the platform region, is set back with respect to the contour running in the blade or vane root, so as to form a recess. To provide a turbine blade or vane which has a service life which is extended with respect to fatigue while at the same time saving cooling air, the invention proposes that the recess, as a partial cavity, is set back so deep into the platform that it lies opposite the platform surface, forming an at least partially hollow platform, and that there is at least one means for diverting the coolant into the partial cavity.
대표청구항
▼
The invention claimed is: 1. A turbine blade or vane for a gas turbine, comprising: a blade or vane root that is successively adjoined by a platform region with a transversely extending platform and then a blade profile that is curved in the longitudinal direction; a platform surface that is provid
The invention claimed is: 1. A turbine blade or vane for a gas turbine, comprising: a blade or vane root that is successively adjoined by a platform region with a transversely extending platform and then a blade profile that is curved in the longitudinal direction; a platform surface that is provided at the platform and exposed to hot gas; and at least one cavity that is open on the root side, through which a coolant can flow and which extends through the blade or vane root and at least into the platform region and is surrounded by an inner wall, and having a contour that extends in the platform region and is set back with respect to a contour extending in the blade or vane root so as to form a recess that widens the cavity, wherein the recess that widens the cavity extends into the region below the platform surface to form an at least partially hollow platform and in that there is at least one means for diverting the coolant into the partial cavity, wherein at least one outlet opening, through which the coolant can flow out of the partial cavity, is provided in the partial cavity for guiding the coolant, wherein the outlet opening opens out into the platform surface or into an end side of the platform, and wherein a pin is located in the cavity and extends from the blade or vane root at least into the platform region, is provided as means for guiding the coolant. 2. The turbine blade or vane as claimed in claim 1, wherein the pin, in the platform region, has a widening, such that the coolant can flow along the pin is diverted in the direction of the partial cavity. 3. The turbine blade or vane as claimed in claim 1, wherein at least one guiding element that is L shaped in cross section extends from the blade or vane root toward the platform region as means for guiding the coolant, with a plurality of limbs of this guiding element, at the end located in the platform region, at least partially projecting into the hollow partial cavity. 4. The turbine blade or vane as claimed in claim 1, wherein at least one guiding element extends from the blade or vane root toward the platform region as means for guiding the coolant, and this guiding element merges into the inner wall, delimiting the cavity, of the blade or vane profile. 5. The turbine blade or vane as claimed in claim 1, wherein the blade or vane root runs in the longitudinal direction of the blade or vane profile and the platform has two platform longitudinal edges bent parallel and extending in the longitudinal direction and the respective blade or vane root surface facing the suction-side and pressure-side profile walls are convexly and concavely curved in a corresponding way to the associated platform longitudinal edges. 6. The turbine blade or vane as claimed in claim 5, wherein the suction-side and/or pressure-side platform overhang is designed as a platform stub with a relatively short platform width. 7. The turbine blade or vane as claimed in claim 5, wherein the blade or vane root is of dovetail, hammer or fir tree shape as seen in cross section. 8. The turbine blade or vane as claimed in claim 1, wherein the blade or vane is cast. 9. The turbine blade or vane as claimed in claim 1, wherein the turbine blade or vane is used in a stationary gas turbine.
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